EASA AD No.: 2012-0063

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0063

Date: 17 April 2012

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation

This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD unless otherwis e specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, A rticle 14(4) exemption]. 

### Type Approval Holder’s Name :
Turboméca Type/Model designation(s) : ARRIEL 1 engines

TCDS Number : EASA E.073

Foreign AD : Not applicable

Supersedure : This AD supersedes EASA AD 2008-0014 dated 17 January 2008.



### ATA 73 Engine Fuel & Control – Fuel Control Unit (FCU) 3-w ay Union Plug – Inspection

Manufacturer(s): Turboméca S.A.
Applicability: ARRIEL 1E2, 1S and 1S1 turboshaft en gines, all serial numbers. These engines are known to be installed on, but not limited to, Eurocopter Deutschland MBB-BK 117 and Sikorsky S-76A helicopte rs.
Reason: A plug adapted for engine bench testing (ca lled “red disk” plug) and not approved for service operation, was inadvertently i nstalled on the engine FCU 3- way union, instead of the sealed plug approved for service operation.This engine was subsequently released for service operat ion and experienced a high pressure leak event (at the fuel pump outlet) due t o cracking of this “red disk“ plug. This condition, if not detected and corrected, coul d lead to in-flight flame-out and/or possibly a fire. Prompted by this occurrence, EASA issued AD 2008-00 14 to require a one-time inspection and corrective action, depending on find ings. Since issuance of AD 2008-0014, it has been determi ned that : - FCU manufactured, repaired or overhauled after 31 March 2008 are not affected. - Some affected FCU might still be held as spares. For the reasons described above, this AD retains th e requirements of EASA AD 2008-0014, which is superseded, limits its applicab ility, and prohibits installation of a FCU on an engine unless it has passed the insp ection and the torque check as required by this AD.EASA AD No.: 2012-0063

EASA Form 110 Page 2/2 Effective Date: 01 May 2012

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within 100 engine hours after the effective dat e of this AD, perform a onetime inspection of the FCU 3-way union plug to dete rmine its compliance, in accordance with the instructions of Turboméca Manda tory Service Bulletin (MSB) 292 73 0817 version D. The definition of a co mpliant plug may be found in paragraph 2.B of the MSB. An FCU that has already been inspected and, depend ing on findings, corrected, as required by EASA AD 2008-0014, or has been manufactured, repaired or overhauled after 31 March 2008, does no t need to be inspected as required by paragraph (1) of this AD. (2) If during the inspection as required by paragra ph (1) of this AD, the plug [P/N 9 932 30 706 0]installed on the FCU 3-way unio n is found compliant, before next flight, verify its torque to be set bet ween 1.3 and 1.5 daN.m in accordance with Turboméca MSB 292 73 0817 version D

. (3) If during the inspection as required by paragra ph (1) of this AD, the plug installed on the FCU 3-way union is found non-compl iant, before next flight, replace it with a compliant plug and adjust its tor que to be set between 1.3 and 1.5 daN.m in accordance with Turboméca MSB 292 73 0817 version D. (4) Inspections and corrective actions, accomplishe d before the effective date of this AD, in accordance with the instructions of Turboméca MSB 292 73 0817 (at any version) are acceptable to comply with the requirements of paragraphs (1), (2) and (3) of this AD. (5) From the effective date of this AD, do not inst all an FCU on an engine or on a helicopter unless it has passed the inspection in accordance with the instructions of Turboméca MSB 292 73 0817 (at any v ersion), or unless the FCU has been manufactured, repaired or overhauled a fter 31 March 2008.

Ref. Publications: Turboméca, S.A. MSB No. 292 73 0 817 version D dated 29 February 2012. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EA SA can accept Alternative Methods of Compliance for this AD. 2. The required actions and the risk allowance have granted the issuance of a Final AD with Request for Comments, postponing the public consultation process after publication. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: Turboméca, S.A., ARRIEL 1 & 2 Customer Support 40220 Tarnos – France Fax: +33 (0)5 59 74 45 15 or contact your nearest technical representative at www.turbomeca-support.com.